EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 500,000 Max Cl/Cd: 102.98 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e853-il-500000-n5.txt Download as CSV file: xf-e853-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5012 0.04228 0.03974 -0.0885 0.9789 0.0033
-8.750 -0.5214 0.03097 0.02762 -0.0942 0.9602 0.0030
-8.500 -0.5113 0.02585 0.02191 -0.0956 0.9490 0.0029
-8.250 -0.4882 0.02253 0.01812 -0.0973 0.9423 0.0029
-8.000 -0.4610 0.02021 0.01544 -0.0989 0.9351 0.0030
-7.750 -0.4269 0.01831 0.01321 -0.1014 0.9306 0.0030
-7.500 -0.3927 0.01673 0.01139 -0.1038 0.9233 0.0031
-7.250 -0.3548 0.01543 0.00987 -0.1068 0.9168 0.0032
-7.000 -0.3194 0.01435 0.00862 -0.1091 0.9066 0.0033
-6.750 -0.2857 0.01344 0.00754 -0.1109 0.8950 0.0035
-6.500 -0.2544 0.01272 0.00664 -0.1121 0.8817 0.0038
-6.250 -0.2255 0.01213 0.00589 -0.1127 0.8680 0.0042
-6.000 -0.1977 0.01169 0.00527 -0.1130 0.8547 0.0046
-5.750 -0.1710 0.01116 0.00460 -0.1131 0.8424 0.0057
-5.500 -0.1441 0.01083 0.00416 -0.1131 0.8309 0.0075
-5.250 -0.1175 0.01048 0.00376 -0.1131 0.8200 0.0132
-5.000 -0.0909 0.01017 0.00344 -0.1131 0.8095 0.0245
-4.750 -0.0641 0.00988 0.00316 -0.1132 0.8001 0.0383
-4.500 -0.0373 0.00959 0.00290 -0.1133 0.7913 0.0604
-4.250 -0.0104 0.00931 0.00264 -0.1133 0.7826 0.0878
-4.000 0.0165 0.00898 0.00240 -0.1135 0.7745 0.1282
-3.750 0.0434 0.00863 0.00217 -0.1137 0.7670 0.1826
-3.500 0.0704 0.00820 0.00194 -0.1140 0.7597 0.2579
-3.000 0.1247 0.00761 0.00173 -0.1144 0.7460 0.4135
-2.750 0.1525 0.00757 0.00168 -0.1144 0.7398 0.4408
-2.500 0.1805 0.00755 0.00164 -0.1145 0.7337 0.4566
-2.250 0.2083 0.00754 0.00160 -0.1145 0.7277 0.4718
-2.000 0.2362 0.00753 0.00158 -0.1146 0.7221 0.4903
-1.750 0.2642 0.00753 0.00158 -0.1147 0.7165 0.5067
-1.250 0.3202 0.00756 0.00154 -0.1148 0.7062 0.5245
-1.000 0.3481 0.00757 0.00153 -0.1149 0.7010 0.5304
-0.750 0.3761 0.00760 0.00153 -0.1150 0.6965 0.5365
-0.500 0.4042 0.00761 0.00154 -0.1151 0.6915 0.5421
-0.250 0.4321 0.00763 0.00156 -0.1151 0.6866 0.5481
0.000 0.4601 0.00767 0.00157 -0.1152 0.6824 0.5542
0.250 0.4881 0.00768 0.00161 -0.1153 0.6777 0.5602
0.500 0.5160 0.00772 0.00164 -0.1154 0.6731 0.5668
0.750 0.5438 0.00775 0.00170 -0.1154 0.6690 0.5730
1.000 0.5718 0.00778 0.00175 -0.1155 0.6644 0.5801
1.250 0.5996 0.00781 0.00182 -0.1156 0.6597 0.5870
1.500 0.6273 0.00787 0.00188 -0.1156 0.6554 0.5945
1.750 0.6549 0.00789 0.00198 -0.1156 0.6495 0.6020
2.000 0.6821 0.00795 0.00205 -0.1155 0.6426 0.6103
2.250 0.7092 0.00798 0.00213 -0.1154 0.6342 0.6189
2.500 0.7359 0.00804 0.00223 -0.1152 0.6251 0.6278
2.750 0.7623 0.00811 0.00232 -0.1149 0.6139 0.6377
3.000 0.7882 0.00817 0.00242 -0.1146 0.5996 0.6480
3.250 0.8137 0.00825 0.00252 -0.1141 0.5810 0.6586
3.500 0.8393 0.00835 0.00264 -0.1137 0.5643 0.6706
3.750 0.8643 0.00847 0.00280 -0.1132 0.5456 0.6836
4.000 0.8887 0.00863 0.00296 -0.1125 0.5206 0.6974
4.250 0.9109 0.00891 0.00317 -0.1115 0.4813 0.7124
4.500 0.9292 0.00945 0.00348 -0.1098 0.4164 0.7293
4.750 0.9431 0.01038 0.00402 -0.1074 0.3259 0.7481
5.000 0.9577 0.01127 0.00459 -0.1053 0.2441 0.7689
5.250 0.9746 0.01196 0.00511 -0.1035 0.1880 0.7933
5.750 1.0079 0.01292 0.00599 -0.0995 0.1166 0.8710
6.000 1.0232 0.01330 0.00636 -0.0971 0.0886 1.0000
6.250 1.0429 0.01387 0.00683 -0.0959 0.0673 1.0000
6.500 1.0629 0.01439 0.00729 -0.0947 0.0514 1.0000
6.750 1.0816 0.01499 0.00780 -0.0933 0.0363 1.0000
7.000 1.0997 0.01561 0.00837 -0.0918 0.0238 1.0000
7.250 1.1173 0.01622 0.00893 -0.0902 0.0150 1.0000
7.500 1.1346 0.01675 0.00947 -0.0885 0.0108 1.0000
7.750 1.1509 0.01732 0.01006 -0.0867 0.0077 1.0000
8.000 1.1652 0.01802 0.01077 -0.0845 0.0053 1.0000
8.250 1.1805 0.01867 0.01149 -0.0825 0.0042 1.0000
8.500 1.1947 0.01940 0.01228 -0.0804 0.0035 1.0000
8.750 1.2068 0.02029 0.01325 -0.0781 0.0029 1.0000
9.000 1.2184 0.02124 0.01429 -0.0757 0.0027 1.0000
9.250 1.2305 0.02216 0.01532 -0.0735 0.0025 1.0000
9.500 1.2420 0.02313 0.01639 -0.0714 0.0025 1.0000
9.750 1.2524 0.02421 0.01761 -0.0692 0.0024 1.0000
10.000 1.2619 0.02539 0.01890 -0.0670 0.0023 1.0000
10.250 1.2702 0.02673 0.02036 -0.0648 0.0022 1.0000
10.500 1.2783 0.02811 0.02186 -0.0627 0.0022 1.0000
10.750 1.2855 0.02964 0.02352 -0.0607 0.0021 1.0000
11.000 1.2922 0.03127 0.02528 -0.0587 0.0021 1.0000
11.250 1.2984 0.03302 0.02716 -0.0569 0.0020 1.0000
11.500 1.3035 0.03494 0.02924 -0.0552 0.0020 1.0000
11.750 1.3082 0.03697 0.03142 -0.0535 0.0020 1.0000
12.000 1.3117 0.03920 0.03381 -0.0520 0.0020 1.0000
12.250 1.3138 0.04163 0.03642 -0.0506 0.0020 1.0000
12.500 1.3150 0.04424 0.03922 -0.0493 0.0019 1.0000
12.750 1.3144 0.04711 0.04227 -0.0482 0.0019 1.0000
13.000 1.3120 0.05028 0.04565 -0.0472 0.0019 1.0000
13.250 1.3079 0.05373 0.04932 -0.0466 0.0019 1.0000
13.500 1.3019 0.05753 0.05333 -0.0462 0.0019 1.0000
13.750 1.2935 0.06179 0.05781 -0.0462 0.0019 1.0000
14.000 1.2842 0.06633 0.06256 -0.0466 0.0019 1.0000
14.250 1.2730 0.07141 0.06783 -0.0476 0.0019 1.0000
14.500 1.2605 0.07697 0.07360 -0.0491 0.0019 1.0000
14.750 1.2460 0.08319 0.08002 -0.0512 0.0019 1.0000
15.000 1.2299 0.09012 0.08716 -0.0542 0.0019 1.0000
15.250 1.2119 0.09798 0.09521 -0.0580 0.0019 1.0000
15.500 1.1923 0.10679 0.10422 -0.0628 0.0019 1.0000
15.750 1.1723 0.11648 0.11410 -0.0685 0.0019 1.0000
16.000 1.1485 0.12812 0.12593 -0.0757 0.0020 1.0000
16.250 1.1225 0.14146 0.13944 -0.0840 0.0020 1.0000
16.500 1.0930 0.15717 0.15530 -0.0933 0.0021 1.0000
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Polar data table (+)
Polar graphs
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